Aeroplane



J. F. WEBB, Sn.

AEROPLANE.

APPLICATION FILED JUNE 8, I9I8. RENEWED FEB.

19 48,43 P j t iited Aug. 3, 1920.

5 SHEETS-SHEET I.

ATTORNEYS AEROPLANE- APPLICATION men JUNE 8.191s.

J. F. WEBB RENEWED FEB- 17-1920.

Patented Aug. 3, 1920.

5 SHEETSSHEET 2.

INVENTOR JMW eZZ) J1 BY M ATTORNEY J. F. WEBB, Sn.

AEROPLANE.

APPLICATION FILED JUNE 8, 1918. RENEWED FEB. 17.1920- Patented Aug. 3, 19%..

' 5 SHEETS-SHEET 3.

J. F. WEBB, Sn.

AEROPLANE.

APPLICATION HLED JUNE 3. IBIB- RENEWED FEB-17.1920.

1 48,463 Patented Aug. 3, 1920..

5 SHEETS-SHEET 4.

INVENTOR JaflWebzv, Jr?

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ATTORNEY J. F. WEBB, SR.

AEROPLANE. APPLICATION FILED JUNE 8.'I9I8- RENEWED FEB. 17.1920.

Patented Aug. 3, 19%.,

5 SHEETSSHEET 5- INVENTOR fiaa val? W$23 J2" JEAN FLWEBB, SR, 0]? NEW YORK, N; Y.

AEROIPLANE.

Application filed June 8, 1918, Serial No. 238,841.

To all whom it may concern:

Be it known that I, JEAN F. WEBB, Sr., av citizen of the United States, residing at New York, in the county of New York and State of New York, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification. v

The present invention relates to the type of aeroplane disclosed in my application Serial No. 201,979, filed November 14, 1917, allowed December 15, 1917 and, as in that case so in the present case, the invention has for its object to provide a practical powerful aeroplane adapted for very heavy duty in commercial use, such as carrying fast,

mail, express, passengers or freight, and to that end the invention provides a structure possessing such unusual lifting and sustaining power that it will support and carry a much greater'weight per given area or number of square feet per plane surface than is possible by those aeroplanes now in general use, and the invention also provides a structure having great flexibility of control while in flight, in rising and landing and onehaving such stability-and steadiness of flight as to render the machine quite safe against unusual air disturbances.

The present invention especially has for its object to provide an aeroplane of the multiplane type (two or more planes) inwhich all of the planes are mounted, substantially at the center of planing pressure, on transverse axes so as to be susceptible of partial rotation about such axes, whereby the inclination of the planes in the direction of flight may be varied to change the angle of incidence at will.

Another object of the invention is to combine, with such tilting planes, auxiliary propeller units which are tiltable with the planes and are designed to add their efforts to increase the lifting andcarrying power of the aeroplane as well as the climbing power and descent thereof, and also to aid in preventing accidents in alighting, as' the angle of the auxiliary propellers and the tiltable planes can be changed in such manner that the speed can be graduated to a slow orsafe landing without jar or shock.

The'invention also has for its especial object to provide sustaining framework for the planes and auxiliary propelling mechanism embodying the maximum Specification of Letters Patent.

Patented Aug. 3,1920. Renewed February 17, 1920. Serial massaam.

side of the fuselage) which is rigidly connected to the fuselage and braced longitudinally by diagonal rods at each side of the fuselage to form, as it'were, longitudinal diamond frames, the longitudinal axial chord of which 'is formed by the fuselage and the upright axial chord of which is formed by the main upright standards so as to establisha rigid frame to support the planes and auxiliary'propelling mechanism. Connecting the various upright frame bars at each side of the fuselage with the main upright frame bars adjacent to the fuselage near the top and bottom of the same, I provide connectin rods which are rigidly secured to the upright bars, thus forming a transverse rectangular frame of rigid structure to sustain the planes. The upper and lower planes, which preferably extend in unbroken area across the width of the machine, are fulcrumed at substantially their center of planing pressure on the upper and lower transverse rods of the transverse rec:v

tangular frame while the intermediate sustaining planes are provided with suitable trunnions located in suitable bearings on the main upright frame bars of the transverse rectangular frame and are linked to: gether with the upper and lower planes to move in unison therewith, the auxiliary propeller shaft housings being rigidly secured to move with the planesin changing their angular relationship to the fuselage with respect to the line of flight.

The invention also includes those novel details of construction, combination and arrangement of parts, all of which will-be first fully described, then be specifically pointed out in the appended claims and illustrated thereof, the upper plane and part of its sustaining mechanism being removed to show gree of the parts beneath.

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Fig. 6 is a detail section and part plan view showing the driving connections with the auxiliary propeller shaft.

Fig. 7 is a detail view showing .the connections for turning the planes to change their angles of incidence.

Fig. 8 is a detail view showing the manner in which the transverse rods of the transverse frame may be rigidly secured to the upright bars.

Fig. 9 is a diagrammatic View showing the manner in which the angle of the planes can be changed.

Fig. 10 is a side elevation of a modification using two sets of sustaining planes, a forward set and a rearward set.

In the drawings, in which like numerals and letters of reference indicate like parts in all of the figures, 1 represents the fuselage which may be of the usual construction as is also the main propeller 2 and its driving mechanism (not shown) the engine shaft 3 having its power transmitted through gears 37, countershafts 36 and gears 36 to the auxiliary propeller shafts 35.

4 designates the tail of the machine, '5 the tail skid and 6 the landing wheels, the latter being braced by front braces 7 extending to the fuselage and rear braces 8 which extend to and connect with the main uprights 11 adjacent to the fuselage, there being cross braces 9 and 10 provided for the usual purpose.

The transverse plane sustaining frame is composed of main uprights 11'11 located one at each side of the fuselage and adapted to be rigidly secured with relation thereto, the intermediate pairs of uprights 16-17 and the end uprights 1 1, theva'rious uprights 111716 and 14 respectively, at each side of the fuselage, being connected rigidly together {by the upper and lower rods 24 which pass through upper and lower coupling parts 23 of the respective uprights and are rigidly secured thereto by collars 26 and set screws 27, the same being preferably threaded together as at 25 (see Fig. 8) thus forming, as it were, a rigid transversely extending frame in the center of which the fusela e is located. In order that the transverse rame may maintain its position relatively fixed with'rela- 'which extends as at 15 to each side of the machine and connects with the lower endsof the respective uprights 17, 16 and 14 to form a lower truss for the plane structure a and the upper ends of the inner uprights 11 may also be connected by across brace 13, if desired. 1

The uprights, 17 16 and 14 are provided with bearings 18 in which the trunnions 19 carried by the midplanes 30, are 'j ournaled.

The inner bars 11 have bearings .18- in which the trunnion portion of the tubular casing 20 that incases the auxiliary propeller countershaft 36 is mounted.

The intermediate planes 30. extend from the fuselage to the extreme outer end of the sustaining planes, being cut away, where necessary, to provide for the passage of the propeller, shaft housing 22 and gear box 21, it being understood that the said' planes 30 are rigidly connected with the gear box 21 and shaft casing 22 to move therewith as a unit. The upper and lower planes 28-29 respectively are provided with suitable bearings to fulcrum on the upper and lower transverse rods 24 of the transverse rectangular frame and they are linked at 31 to the central plane 30 and auxiliary propeller shaft housing 22 in order thatthe planes 28-2930 and propeller shaft housing 22 will maintain their parallelism and be shiftable on the respective axes 2424 (see Fig. 1) to change the angle of incidence. The links 31 are pivoted at 32 to the upper and lower planes and at 33 to the intermediate plane or shaft housing adjacent to both the front and back ends of the planes, and at the lateral extremities thereof and also adjacent to the fuselage (see Fig. 8). 34 designates diagonal cross wires at the front and back edges, of the planes for bracing the same to maintain parallelism between the front and back edges respectively of the several planes.

35 "designates the propeller shaft which is geared at 36' to the countershaft 36 that is connected by bevel gears 37 with the en? gine shaft 3.

In order to tilt the planes 28--30-29 on their axes to change the angle of incidence (and in practice a 20. change either away anism may be provided and as the same confrom the neutral or central position is usually sufiicient for the purpose) I provide spur tubes 20 to which the intermediate planes are rigidly secured, which gears 38 mesh with gears 40 on a countershaft 39 that carries a worm gear 41 with which the worm 42 on the control shaft 43, meshes. By turning shaft 43 through the medium of the hand wheel, the shaft 39 will be rocked to correspondingly rock the tubular rods or sleeves 20 and thereby rock the central plane 30, auxiliary propeller shaft housing 22 and upper and lower planes 28 and 29, respectively, as a unit.

In Fig. 10, I have shown a modification of the invention in which two sets of sustaining planes, one forward and one aft, maybe employed, and while I have shown only one set of auxiliary propeller mechanism on the forward set of planes, yet it may be understood that the same may be duplicated on the rear set of planes, the two sets of planes being mounted correspondingly and designed to move in unison. by virtue of the levers 49 and connecting rods 48 whereby as the forward set of planes are manipulated the rearward set will be correspondingly manipulated. In this form also the diamond frame is lengthened out and provided with longitudinal extension connecting rods 47 between the front and rear sets of uprights 11.

Other changes in the details of construction, design and arrangement of parts can be readily made without departing from the spirit of. the invention or the scope of the appended claims.

While I have shown the invention as a triplane'structure, yet'it is evident that the midplane may be omitted and the structure made as a biplane structure, or additional planes may be provided, as found desirable in practice.

Also any suitable lateral control mechstitutes no part of my invention I have not undertaken a detail illustration or description of the same,a well-known form of lateral control mechanism is, however, indicated in the drawings by the reference numeral 50.

What I claim is j 1. In an aeroplane, a rigid frame structure comprising in combination with the fuselage a transverse rectangular frame including uprights adjacent to the fuselage and end uprights at the lateral extremities,

transverse connecting rods secured to the.

several uprights, a bottom truss brace between the end uprights and the uprights adjacent to the fuselage, and forwardly and rearwardly extending rigid diagonal braces connecting the upper and lower extremities of the uprights, which are adjacent to the gears 38 on the trunnion ends of the r fuselage,-with the fuselage, and sustaining planes mounted on the said transverse rectangular frame.

2. In an aeroplane, a rigid frame structure comprising in. combination with the fuselage, a transverse rectangular frame including uprights adjacent to thafuselage, and end uprights at'the lateral extremities, transverse connecting rods secured to the several uprights, a bottom truss brace between the'end uprights and the uprights adjacent to the fuselage, forwardly and rearwardly extending rigid diagonal braces connecting the upper and lower extremities of the uprights, which are adjacent to the fuselage with the fuselage, upper and lower sustaining planes pivoted on the upper and lower transverse bars of said transverse frame at approximately the center of planing pressure, link connections between the upper and lower sustaining planes whereby they will move in unison and means under the control of the operator for moving said planes on their pivots to change the angle of incidence.

3. In an aeroplane, a frame structure com prising in combination, with the fuselage, a transverse rectangular frame including uprights adjacent to the fuselage and end uprights at the lateral extrem1ties,a bottom '95 truss brace between the end uprights and braces connecting the upper and lower extremities of the uprights, which are adjacent to the fuselage, with the fuselage, upper and lower sustaining planes pivoted on the upper and,lower transverse bars of said transverse frame at approximately the center of. plan.- ing pressure,link connections between the upper and lower sustaining planes whereby they will move in unison and means under the control of the operator for moving said planes on their pivots to change the angle of incidence, a main propelling mechanism carried by the fuselage, auxiliary propellers mounted between the upper-and lower sustaining planes and connected therewith to move in unison with the same whereby as the angle of incidence of the planes is changed the axes of the auxiliary propellers will be correspondingly changed.

4. In an aeroplane structure, rigid diamond-shaped trusses extending substantially parallel with the fuselage, interlocked at right angles with a. rigid transverse cross truss to form a supporting framework for the fuselage, engines and planes.

5. In 'an aeroplane structure, a double rigid framework consisting of a pair of diamond-shaped trusses arranged substantially parallel with the fuselage, and transverse trusses, the said diamond-shaped trusses and transverse trusses being connected with each other at right angles and to the fuselage in such manner that the whole forms a rigid support in both directions for the fuselage, engines and planes.

6. In an aeroplane structure, a framing comprising, in combination with the fuselage frame a transverse rectangular frame structure consisting of uprights and transverse connecting rods between said uprights, and diagonal rods connecting said transverse frame with the fuselage, said diagonal rods and the adjacent uprights forming with the fuselage, diamond frames having axial chords formed by the fuselage and adjacent uprights respectively, upper and lower sustaining planes pivotally mounted on transverse axes on said transverse frame, and extending across the width of the machine, a main propeller mechanism carried by the fuselage, auxiliary propeller mechanism located in a plane parallel to that containing the main propeller, means for sustaining said auxiliary propeller structure pivotally on an axis transversely of the aeroplane, and means for connecting the upper and lower sustaining planes with said auxiliary propeller'mechanism whereby the degree of inclination of the upper and lower sustaining planes will be imparted to the auxiliary propeller mechanism, and means for varying the angle of incidence of the sustaining planes.

"7. In an aeroplane structure, a framing comprising, in combination with the fuselage frame, a transverse rectangular frame structure consisting of uprights and transverse connecting rods between said uprights, and diagonal rods connecting said transverse frame with the fuselage, said diagonal rods and the adjacent u ri hts forming, with the fuselage, diamon rames having axial chords formed by the fuselage and adjacent uprights respectively, upper and lower sustaining planes pivotally mounted on transverse axes on said transverse frame, and extending across the width ofthe machine, a main propeller mechanism carried by the fuselage, auxiliary propeller mechanism located 1n a plane parallel to that containing the main propeller, means for sustaining said auxiliary propeller structurepivotally on an axis transversely of the aero lane, means for connecting the upper and ower sustaining planes with said auxiliary propeller mechanism whereby the degree of inclination of the upper and lower sustaining planes will be imparted to the auxiliary propeller mechanism, means for varying the angle of incidence of the sustaining planes, an intermediate sustaining plane mounted between the upper and lower sustaining planes and connected therewith to move in unison with the same.

8. The combination in an aeroplane structure, of rigid diamond shaped trusses and rigid transverse trusses crossing each other at right angles and interlocked together and with the fuselage framework to form a support, longitudinally and transversely, for

JEAN F. WEBB, s15. 

